FR3078367B1 - TURBOMACHINE WITH A HEAT EXCHANGER IN THE SECONDARY VEIN - Google Patents

TURBOMACHINE WITH A HEAT EXCHANGER IN THE SECONDARY VEIN Download PDF

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Publication number
FR3078367B1
FR3078367B1 FR1851624A FR1851624A FR3078367B1 FR 3078367 B1 FR3078367 B1 FR 3078367B1 FR 1851624 A FR1851624 A FR 1851624A FR 1851624 A FR1851624 A FR 1851624A FR 3078367 B1 FR3078367 B1 FR 3078367B1
Authority
FR
France
Prior art keywords
pressure compressor
turbomachine
pressurized air
heat exchanger
stream
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related
Application number
FR1851624A
Other languages
French (fr)
Other versions
FR3078367A1 (en
Inventor
Catherine Pikovsky
Christophe Marcel Lucien Perdrigeon
Cedric Zaccardi
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1851624A priority Critical patent/FR3078367B1/en
Priority to EP19710756.8A priority patent/EP3735518B1/en
Priority to US16/970,815 priority patent/US11686249B2/en
Priority to PCT/FR2019/050358 priority patent/WO2019162601A1/en
Priority to CN201980013760.7A priority patent/CN111727302B/en
Publication of FR3078367A1 publication Critical patent/FR3078367A1/en
Application granted granted Critical
Publication of FR3078367B1 publication Critical patent/FR3078367B1/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
    • F02C7/143—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F02C7/185—Cooling means for reducing the temperature of the cooling air or gas
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
    • F02K3/105—Heating the by-pass flow
    • F02K3/115—Heating the by-pass flow by means of indirect heat exchange
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/047—Heating to prevent icing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/213—Heat transfer, e.g. cooling by the provision of a heat exchanger within the cooling circuit
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/98—Lubrication
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne une turbomachine (10) d'aéronef comportant une veine primaire (16) d'écoulement d'air dans laquelle sont aménagés un compresseur basse pression (30) et un compresseur haute pression (32), une veine secondaire (20) d'écoulement d'air qui est située autour de la veine primaire (16) et coaxialement à la veine primaire (16), comportant une pluralité d'aubes réparties autour d'un axe principal (A) de la turbomachine (10), un circuit d'air pressurisé (40) prélevant de l'air entre le compresseur basse pression (30) et le compresseur haute pression (32) ou dans le compresseur haute pression qui alimente au moins un composant (12) situé à proximité d'un axe principal (A) de la turbomachine, dans laquelle le circuit d'air pressurisé (40) comporte un échangeur de chaleur (44) entre le flux d'air pressurisé et le flux d'air s'écoulant dans la veine secondaire (20), qui est agencé dans au moins une aube (54) du redresseur, caractérisée en ce que l'échangeur de chaleur comporte une conduite agencée dans ladite au moins une aube (54), qui comporte une entrée d'air pressurisé (62) et une sortie d'air pressurisé (64) qui sont situées à une même extrémité radiale (56) de ladite aube (54).The invention relates to an aircraft turbomachine (10) comprising a primary air flow stream (16) in which a low pressure compressor (30) and a high pressure compressor (32) are arranged, a secondary stream (20). ) air flow which is located around the primary stream (16) and coaxially with the primary stream (16), comprising a plurality of vanes distributed around a main axis (A) of the turbomachine (10) , a pressurized air circuit (40) taking air between the low pressure compressor (30) and the high pressure compressor (32) or in the high pressure compressor which supplies at least one component (12) located in the vicinity of 'a main axis (A) of the turbomachine, in which the pressurized air circuit (40) comprises a heat exchanger (44) between the pressurized air flow and the air flow flowing in the secondary stream (20), which is arranged in at least one blade (54) of the rectifier, characterized in that the heat exchanger comprises a pipe arranged in said at least one blade (54), which comprises a pressurized air inlet (62) and a pressurized air outlet (64) which are located at the same radial end (56) of said blade (54) ).

FR1851624A 2018-02-23 2018-02-23 TURBOMACHINE WITH A HEAT EXCHANGER IN THE SECONDARY VEIN Expired - Fee Related FR3078367B1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
FR1851624A FR3078367B1 (en) 2018-02-23 2018-02-23 TURBOMACHINE WITH A HEAT EXCHANGER IN THE SECONDARY VEIN
EP19710756.8A EP3735518B1 (en) 2018-02-23 2019-02-18 Turbine engine comprising a heat exchanger in the bypass flowpath
US16/970,815 US11686249B2 (en) 2018-02-23 2019-02-18 Turbine engine comprising a heat exchanger in the secondary path
PCT/FR2019/050358 WO2019162601A1 (en) 2018-02-23 2019-02-18 Turbine engine comprising a heat exchanger in the secondary path
CN201980013760.7A CN111727302B (en) 2018-02-23 2019-02-18 Turbine engine including a heat exchanger in the secondary path

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1851624A FR3078367B1 (en) 2018-02-23 2018-02-23 TURBOMACHINE WITH A HEAT EXCHANGER IN THE SECONDARY VEIN
FR1851624 2018-02-23

Publications (2)

Publication Number Publication Date
FR3078367A1 FR3078367A1 (en) 2019-08-30
FR3078367B1 true FR3078367B1 (en) 2021-09-03

Family

ID=62222925

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1851624A Expired - Fee Related FR3078367B1 (en) 2018-02-23 2018-02-23 TURBOMACHINE WITH A HEAT EXCHANGER IN THE SECONDARY VEIN

Country Status (5)

Country Link
US (1) US11686249B2 (en)
EP (1) EP3735518B1 (en)
CN (1) CN111727302B (en)
FR (1) FR3078367B1 (en)
WO (1) WO2019162601A1 (en)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2599686A (en) * 2020-10-09 2022-04-13 Rolls Royce Plc An improved turbofan gas turbine engine
US11965697B2 (en) 2021-03-02 2024-04-23 General Electric Company Multi-fluid heat exchanger
FR3130876A1 (en) 2021-12-20 2023-06-23 Safran Aircraft Engines Rectifier blade comprising a heat pipe
US11873758B1 (en) * 2022-10-28 2024-01-16 Pratt & Whitney Canada Corp. Gas turbine engine component with integral heat exchanger
US11927134B1 (en) 2023-01-27 2024-03-12 General Electric Company Gas turbine engine having a heat exchanger located in an annular duct
CN117569923B (en) * 2024-01-12 2024-04-05 成都中科翼能科技有限公司 Turbine fulcrum structure of gas turbine

Family Cites Families (18)

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Publication number Priority date Publication date Assignee Title
FR1093301A (en) * 1953-02-17 1955-05-03
GB1244340A (en) * 1968-12-23 1971-08-25 Rolls Royce Front fan gas turbine engine
US4645415A (en) * 1983-12-23 1987-02-24 United Technologies Corporation Air cooler for providing buffer air to a bearing compartment
US4542623A (en) * 1983-12-23 1985-09-24 United Technologies Corporation Air cooler for providing buffer air to a bearing compartment
GB2192229B (en) * 1986-07-04 1990-05-02 Rolls Royce Plc A compressor and air bleed system
US4914904A (en) * 1988-11-09 1990-04-10 Avco Corporation Oil cooler for fan jet engines
FR2734320B1 (en) 1995-05-15 1997-07-18 Aerospatiale DEVICE FOR TAKING UP AND COOLING HOT AIR AT AN AIRCRAFT ENGINE
AU2001213231A1 (en) * 2000-11-10 2002-05-21 Marek Kovac Bypass gas turbine engine and cooling method for working fluid
GB0719786D0 (en) * 2007-10-11 2007-11-21 Rolls Royce Plc A vane and a vane assembly for a gas turbine engine
US9945325B2 (en) 2013-02-20 2018-04-17 United Technologies Corporation Integrated heat exchangers for low fan pressure ratio geared turbofan
US10337406B2 (en) * 2013-02-28 2019-07-02 United Technologies Corporation Method and apparatus for handling pre-diffuser flow for cooling high pressure turbine components
GB201415078D0 (en) * 2014-08-26 2014-10-08 Rolls Royce Plc Gas turbine engine anti-icing system
US20160369697A1 (en) * 2015-06-16 2016-12-22 United Technologies Corporation Cooled cooling air system for a turbofan engine
US10563582B2 (en) * 2016-01-19 2020-02-18 United Technologies Corporation Heat exchanger array
US10316681B2 (en) * 2016-05-31 2019-06-11 General Electric Company System and method for domestic bleed circuit seals within a turbine
US10837364B2 (en) * 2017-01-27 2020-11-17 Raytheon Technologies Corporation Thermal shield for gas turbine engine diffuser case
US10830056B2 (en) * 2017-02-03 2020-11-10 General Electric Company Fluid cooling systems for a gas turbine engine
US11725584B2 (en) * 2018-01-17 2023-08-15 General Electric Company Heat engine with heat exchanger

Also Published As

Publication number Publication date
EP3735518A1 (en) 2020-11-11
US11686249B2 (en) 2023-06-27
CN111727302B (en) 2023-04-11
EP3735518B1 (en) 2021-12-29
US20210115854A1 (en) 2021-04-22
WO2019162601A1 (en) 2019-08-29
CN111727302A (en) 2020-09-29
FR3078367A1 (en) 2019-08-30

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